Abstract
The use of a full 3D and viscous inverse method for turbomachine blading with splitter blades is demonstrated by carrying out a design modification of a transonic axial stator blade row with splitter blades. In this design modification study, the goal is to improve the aerodynamics of the full blade and the splitter blade, including weakening of shock wave and control of flow incidence. The improved blade design is "validated" using a well-known 3D Navier-Stokes analysis solver.
| Original language | English (US) |
|---|---|
| Title of host publication | Aircraft Engine; Marine; Turbomachinery; Microturbines and Small Turbomachinery |
| Publisher | American Society of Mechanical Engineers (ASME) |
| Volume | 1 |
| ISBN (Print) | 9780791878545, 9780791878545 |
| DOIs | |
| State | Published - 2000 |
| Event | ASME Turbo Expo 2000: Power for Land, Sea, and Air, GT 2000 - Munich, Germany Duration: May 8 2000 → May 11 2000 |
Other
| Other | ASME Turbo Expo 2000: Power for Land, Sea, and Air, GT 2000 |
|---|---|
| Country | Germany |
| City | Munich |
| Period | 5/8/00 → 5/11/00 |
ASJC Scopus subject areas
- Engineering(all)
Fingerprint Dive into the research topics of '3D inverse method for turbomachine blading with splitter blades'. Together they form a unique fingerprint.
Cite this
Qiu, X., & Dang, T. Q. (2000). 3D inverse method for turbomachine blading with splitter blades. In Aircraft Engine; Marine; Turbomachinery; Microturbines and Small Turbomachinery (Vol. 1). American Society of Mechanical Engineers (ASME). https://doi.org/10.1115/2000-GT-0526